EPPLER 339 AIRFOIL (e339-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 339 AIRFOIL (e339-il) Reynolds number: 1,000,000 Max Cl/Cd: 116.64 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e339-il-1000000-n5.txt Download as CSV file: xf-e339-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 339 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.1454 0.07721 0.07413 -0.0568 0.5824 0.0058
-9.000 -0.1919 0.07867 0.07545 -0.0665 0.5919 0.0056
-8.750 -0.1918 0.07560 0.07237 -0.0679 0.5832 0.0054
-8.500 -0.1953 0.07191 0.06868 -0.0699 0.5762 0.0053
-8.250 -0.2072 0.06749 0.06427 -0.0732 0.5702 0.0052
-8.000 -0.2198 0.06409 0.06084 -0.0735 0.5633 0.0050
-7.750 -0.2308 0.06128 0.05799 -0.0722 0.5578 0.0050
-7.500 -0.2393 0.05719 0.05383 -0.0716 0.5522 0.0048
-7.250 -0.2450 0.05295 0.04948 -0.0705 0.5463 0.0046
-7.000 -0.2496 0.04817 0.04455 -0.0687 0.5417 0.0044
-6.750 -0.2510 0.04341 0.03961 -0.0664 0.5366 0.0044
-6.500 -0.2552 0.03737 0.03327 -0.0628 0.5315 0.0042
-6.250 -0.2447 0.03437 0.03007 -0.0607 0.5251 0.0044
-6.000 -0.2351 0.03067 0.02612 -0.0580 0.5185 0.0046
-5.750 -0.2488 0.01849 0.01282 -0.0497 0.5176 0.0053
-5.250 -0.2049 0.01561 0.00936 -0.0473 0.5023 0.0055
-5.000 -0.1806 0.01480 0.00837 -0.0466 0.4950 0.0056
-4.750 -0.1559 0.01406 0.00746 -0.0458 0.4888 0.0056
-4.500 -0.1306 0.01350 0.00678 -0.0453 0.4820 0.0057
-4.000 -0.0802 0.01251 0.00556 -0.0441 0.4688 0.0060
-3.750 -0.0553 0.01206 0.00501 -0.0434 0.4618 0.0061
-3.500 -0.0303 0.01166 0.00454 -0.0428 0.4561 0.0061
-3.250 -0.0052 0.01128 0.00411 -0.0421 0.4508 0.0062
-3.000 0.0200 0.01099 0.00376 -0.0415 0.4452 0.0062
-2.750 0.0453 0.01075 0.00346 -0.0410 0.4401 0.0063
-2.500 0.0710 0.01051 0.00319 -0.0404 0.4352 0.0064
-2.250 0.0966 0.01032 0.00295 -0.0399 0.4295 0.0065
-2.000 0.1223 0.01016 0.00275 -0.0394 0.4242 0.0067
-1.750 0.1486 0.01001 0.00257 -0.0390 0.4202 0.0068
-1.500 0.1748 0.00988 0.00241 -0.0386 0.4158 0.0073
-1.250 0.2011 0.00978 0.00227 -0.0382 0.4114 0.0077
-1.000 0.2274 0.00970 0.00215 -0.0379 0.4071 0.0083
-0.750 0.2541 0.00960 0.00205 -0.0376 0.4034 0.0103
-0.500 0.2806 0.00952 0.00197 -0.0373 0.3989 0.0144
-0.250 0.3068 0.00944 0.00192 -0.0369 0.3949 0.0270
0.000 0.3330 0.00938 0.00189 -0.0366 0.3911 0.0457
0.250 0.3588 0.00920 0.00187 -0.0362 0.3884 0.0956
0.500 0.3639 0.00732 0.00172 -0.0326 0.3857 0.6710
0.750 0.3779 0.00698 0.00203 -0.0292 0.3824 0.8781
1.000 0.4038 0.00712 0.00213 -0.0286 0.3785 0.8910
1.250 0.4297 0.00726 0.00222 -0.0280 0.3750 0.8986
1.500 0.4548 0.00739 0.00234 -0.0272 0.3728 0.9074
1.750 0.4796 0.00752 0.00247 -0.0263 0.3697 0.9144
2.000 0.5073 0.00759 0.00248 -0.0263 0.3662 0.9157
2.250 0.5350 0.00766 0.00250 -0.0264 0.3629 0.9167
2.500 0.5627 0.00774 0.00254 -0.0264 0.3596 0.9175
2.750 0.5908 0.00779 0.00256 -0.0265 0.3569 0.9182
3.000 0.6189 0.00784 0.00260 -0.0267 0.3541 0.9188
3.250 0.6468 0.00791 0.00264 -0.0268 0.3511 0.9193
3.500 0.6745 0.00799 0.00268 -0.0269 0.3479 0.9199
3.750 0.7016 0.00807 0.00274 -0.0268 0.3445 0.9206
4.000 0.7288 0.00814 0.00280 -0.0268 0.3419 0.9214
4.250 0.7562 0.00820 0.00286 -0.0268 0.3394 0.9222
4.500 0.7834 0.00828 0.00294 -0.0268 0.3361 0.9229
4.750 0.8104 0.00837 0.00301 -0.0268 0.3328 0.9236
5.000 0.8370 0.00848 0.00310 -0.0267 0.3293 0.9243
5.250 0.8639 0.00858 0.00319 -0.0267 0.3264 0.9250
5.500 0.8911 0.00866 0.00329 -0.0268 0.3237 0.9257
5.750 0.9180 0.00875 0.00339 -0.0267 0.3200 0.9264
6.000 0.9444 0.00887 0.00349 -0.0267 0.3161 0.9272
6.250 0.9703 0.00901 0.00362 -0.0265 0.3123 0.9281
6.500 0.9972 0.00910 0.00373 -0.0265 0.3092 0.9289
6.750 1.0236 0.00921 0.00385 -0.0265 0.3051 0.9297
7.000 1.0494 0.00935 0.00399 -0.0264 0.3003 0.9306
7.250 1.0751 0.00950 0.00414 -0.0262 0.2955 0.9315
7.500 1.1009 0.00963 0.00428 -0.0261 0.2902 0.9325
7.750 1.1257 0.00982 0.00445 -0.0258 0.2840 0.9335
8.000 1.1512 0.00997 0.00462 -0.0257 0.2793 0.9344
8.250 1.1760 0.01013 0.00479 -0.0254 0.2738 0.9353
8.500 1.1994 0.01033 0.00499 -0.0249 0.2676 0.9364
8.750 1.2235 0.01049 0.00518 -0.0245 0.2618 0.9374
9.000 1.2458 0.01074 0.00541 -0.0238 0.2544 0.9387
9.250 1.2682 0.01097 0.00565 -0.0231 0.2456 0.9399
9.500 1.2891 0.01126 0.00592 -0.0222 0.2360 0.9414
9.750 1.3088 0.01161 0.00623 -0.0211 0.2255 0.9431
10.000 1.3286 0.01192 0.00654 -0.0201 0.2153 0.9448
10.250 1.3472 0.01228 0.00688 -0.0188 0.2055 0.9467
10.500 1.3630 0.01265 0.00724 -0.0171 0.1962 0.9488
10.750 1.3744 0.01308 0.00765 -0.0145 0.1848 0.9519
11.000 1.3867 0.01350 0.00807 -0.0121 0.1748 0.9556
11.250 1.3969 0.01402 0.00857 -0.0095 0.1634 0.9606
11.500 1.4072 0.01458 0.00912 -0.0070 0.1529 0.9663
11.750 1.4146 0.01550 0.00996 -0.0047 0.1349 0.9754
12.250 1.4368 0.01759 0.01195 -0.0024 0.1059 1.0000
12.500 1.4406 0.01868 0.01302 -0.0001 0.0969 1.0000
12.750 1.4419 0.02001 0.01433 0.0021 0.0878 1.0000
13.000 1.4410 0.02163 0.01593 0.0042 0.0783 1.0000
13.250 1.4507 0.02269 0.01706 0.0052 0.0776 1.0000
13.500 1.4437 0.02504 0.01939 0.0069 0.0665 1.0000
13.750 1.4466 0.02685 0.02124 0.0077 0.0631 1.0000
14.000 1.4423 0.02936 0.02377 0.0086 0.0567 1.0000
14.250 1.4319 0.03260 0.02701 0.0093 0.0488 1.0000
14.500 1.4265 0.03550 0.02996 0.0097 0.0449 1.0000
14.750 1.4258 0.03806 0.03258 0.0098 0.0432 1.0000
15.000 1.4156 0.04160 0.03616 0.0099 0.0386 1.0000
15.250 1.4060 0.04520 0.03980 0.0098 0.0350 1.0000
15.500 1.4080 0.04764 0.04235 0.0096 0.0359 1.0000
15.750 1.4003 0.05121 0.04597 0.0092 0.0334 1.0000
16.000 1.3895 0.05525 0.05006 0.0086 0.0302 1.0000
16.250 1.3853 0.05861 0.05350 0.0080 0.0290 1.0000
16.500 1.3775 0.06249 0.05743 0.0073 0.0268 1.0000
16.750 1.3701 0.06642 0.06143 0.0064 0.0251 1.0000
17.000 1.3581 0.07100 0.06604 0.0052 0.0215 1.0000
17.250 1.3521 0.07492 0.07002 0.0042 0.0201 1.0000
17.500 1.3474 0.07872 0.07389 0.0030 0.0192 1.0000
17.750 1.3421 0.08266 0.07789 0.0018 0.0178 1.0000
18.000 1.3360 0.08677 0.08207 0.0004 0.0166 1.0000
18.250 1.3303 0.09091 0.08627 -0.0010 0.0154 1.0000
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Polar data table (+)
Polar graphs
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